Approximate analytical solutions to fuel-optimal reconfiguration problems in perturbed relative motion between satellite

다국어 초록 (Multilingual Abstract)

In this thesis, new analytical solutions to optimal reconfiguration problems in formation flying are developed, including perturbations such as the differential gravity effects, the eccentricity effects of a reference orbit, and J2 effects. The perturbation approach and the calculus of variations are applied to the optimal reconfiguration problems in order to obtain an approximate analytical solution. Some nonlinear relative dynamics are also presented to contain nonlinear terms due to each perturbation. For the sake of validity, numerical simulations are performed for satellite reconfiguration cases in which the distance between the satellites is large and the reference orbit is eccentric. The improved accuracies of the new analytical solutions ensuring reasonable fuel usage are confirmed and the magnitude of the errors caused by each perturbation is compared and analyzed. It is found that the accuracy improvement of the new analytical solutions dealing with the eccentricity effects of a reference orbit is the most prominent. This shows that the eccentricity effects of a reference orbit prevail over the other two perturbations. Finally, it is confirmed that more accurate analytical solutions to fuel-optimal reconfiguration problems including perturbations can be obtained by the method developed in this study and this method makes it possible to more precisely analyze the effects of perturbations on satellite reconfiguration problems.